HEAT TRANSFER ON AXISYMMETRIC ROCKET NOSE CONES WITH SEPARATIONLESS AND SEPARATED FLOWS.

Design of aerophysical sounding rockets equipped with measuring systems, multichannel standard telemetry, temperature and pressure transducers is discussed. An economical technique was developed for computer calculation of the thermal state of axisymmetrical cones. It corrects for variations in the modes of boundary-layer flow, and gives satisfactory agreement between predicted and in-flight data. Heat fluxes were calculated from in-flight transient wall temperatures, using smoothing by means of cubic splines and the 'thin-wall' model.